Patent GB-710252-A (GB)
Title: Improvements in or relating to power plants incorporating gas turbines
Inventor: MORLEY ARNOLD WILLIAM
IPC: F02C5/12
Filed: 1950-05-25
Abstract: 710,252. Gas turbine plant; motor power plant; jet propulsion plant. NAPIER & SON, Ltd., D. Aug. 24, 1951 [May 25, 1950], No. 13226/50. Class 110(3) [Also in Group XII] In a power plant comprising means A for delivering compressed air with or without products of combustion to a plurality of combustion chambers in which the air is partly or wholly burnt with fuel prior to driving a gas turbine E, the combustion chambers are arranged in two or more groups each consisting of two or more combustion chambers mounted to rotate bodily about an axis equidistant from the axes of the combustion chambers constituting said group so as to bring the inlet and outlet ports of each of the combustion chambers of said group in turn into communication with a fixed air delivery port and a fixed gas discharge port respectively; constant volume combustion being effected in the combustion chambers during periods when it is: cut off from both ports. Each group of combustion chambers is supported between end plates H, H<SP>1</SP> which are screwthreaded on a shaft J. The shafts J are journaled in plates B, G and each plate H, H<SP>1</SP> is urged thereagainst by a spring J<SP>2</SP>. Each plate H. H<SP>1</SP> has three tubular extensions H<SP>4</SP>, H<SP>5</SP>, which together with tubular shells H<SP>6</SP> form the combustion chambers of the group. The shafts J are driven by the turbine shaft C through a shaft K journaled in a casing L on the plate B and intermediate gearing as shown. Ignition is effected by the heat of the air or by igniting plugs M mounted in the combustion chambers or on the plate B. Each outlet port H<SP>3</SP> is angularly displaced with respect to each inlet port H<SP>2</SP> or is in line therewith in which case the nozzle ports F<SP>1</SP> are angularly displaced about the shaft J with respect to ports A<SP>3</SP>. Moreover the opening of the ports H<SP>2</SP>, A3 in each group overlap to provide a constant port area therefor. In a modification each of the ports F<SP>1</SP> is divided into two sections which respectively come into communication with the ports H<SP>3</SP> to feed first and second turbine stages respectively.. The exhaust gases from the. first turbine stage are fed to the second turbine stage. The fuel is injected directly. into the combustion chambers or a part or the whole of the fuel is injected into the air as or before it enters the combustion chamber. The compressor may be driven by the turbine or separately driven. It is stated in the Provisional Specification that the internal combustion engine may produce useful power and that the invention is also applicable to power plants in which the groups of combustion chambers are disposed between two turbines or two stages of a turbine. In such cases the first turbine or turbine stage is fed with combustion products from the internal combustion engine or from combustion chambers.supplied with excess air from an air compressor whilst the second turbine or turbine stage receives its working fluid from the group of combustion chambers in which a further proportion of the air is burnt. When applied to a jet propulsion plant the turbine may drive a compressor only and exhaust from the turbine passes to a jet propulsion nozzle or in addition the turbine may drive a propeller. The term turbine includes a single stage or a multi-stage turbine and two or more turbines having separate rotors geared together or not and either arranged in series or parallel. The term compressor includes axial-flow compressors and centrifugal compressors or a combination thereof. This subject matter does not appear in the Complete Specification.